S2027 (s2027-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2027 (s2027-il) Reynolds number: 200,000 Max Cl/Cd: 70.07 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2027-il-200000-n5.txt Download as CSV file: xf-s2027-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2027
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5208 0.08258 0.07884 -0.0470 1.0000 0.0166
-12.000 -0.5495 0.07217 0.06834 -0.0545 1.0000 0.0164
-11.750 -0.5705 0.06464 0.06069 -0.0604 1.0000 0.0163
-11.500 -0.5931 0.05794 0.05384 -0.0656 1.0000 0.0162
-11.250 -0.6114 0.05282 0.04855 -0.0690 1.0000 0.0162
-11.000 -0.6282 0.04862 0.04418 -0.0710 1.0000 0.0161
-10.750 -0.6430 0.04532 0.04071 -0.0715 1.0000 0.0161
-10.500 -0.6598 0.04279 0.03802 -0.0699 1.0000 0.0161
-10.250 -0.6609 0.03974 0.03466 -0.0704 0.9804 0.0162
-10.000 -0.6479 0.03654 0.03104 -0.0724 0.9630 0.0163
-9.750 -0.6322 0.03396 0.02807 -0.0733 0.9487 0.0164
-9.500 -0.6160 0.03189 0.02563 -0.0733 0.9353 0.0166
-9.250 -0.5997 0.02969 0.02321 -0.0729 0.9234 0.0169
-8.750 -0.5641 0.02668 0.01987 -0.0713 0.9010 0.0174
-8.500 -0.5455 0.02548 0.01853 -0.0703 0.8905 0.0177
-8.250 -0.5261 0.02449 0.01741 -0.0693 0.8811 0.0183
-8.000 -0.5059 0.02363 0.01640 -0.0684 0.8710 0.0191
-7.750 -0.4850 0.02273 0.01537 -0.0675 0.8618 0.0198
-7.500 -0.4641 0.02180 0.01429 -0.0665 0.8532 0.0204
-7.250 -0.4426 0.02090 0.01328 -0.0656 0.8436 0.0207
-7.000 -0.4210 0.02008 0.01233 -0.0647 0.8355 0.0211
-6.750 -0.3990 0.01931 0.01146 -0.0638 0.8264 0.0215
-6.500 -0.3783 0.01841 0.01048 -0.0629 0.8178 0.0222
-6.250 -0.3562 0.01772 0.00972 -0.0622 0.8094 0.0229
-6.000 -0.3329 0.01713 0.00905 -0.0616 0.8008 0.0239
-5.750 -0.3092 0.01661 0.00841 -0.0609 0.7928 0.0251
-5.500 -0.2846 0.01615 0.00784 -0.0605 0.7840 0.0268
-5.250 -0.2603 0.01566 0.00726 -0.0599 0.7763 0.0294
-5.000 -0.2352 0.01522 0.00677 -0.0595 0.7674 0.0336
-4.750 -0.2103 0.01474 0.00625 -0.0590 0.7595 0.0416
-4.500 -0.1857 0.01417 0.00576 -0.0587 0.7509 0.0681
-4.250 -0.1614 0.01359 0.00536 -0.0583 0.7429 0.1149
-4.000 -0.1369 0.01304 0.00501 -0.0580 0.7345 0.1721
-3.750 -0.1133 0.01237 0.00471 -0.0577 0.7264 0.2611
-3.500 -0.0889 0.01189 0.00448 -0.0574 0.7182 0.3389
-3.250 -0.0641 0.01150 0.00436 -0.0570 0.7098 0.4149
-3.000 -0.0387 0.01128 0.00428 -0.0565 0.7021 0.4758
-2.750 -0.0121 0.01118 0.00422 -0.0562 0.6933 0.5145
-2.500 0.0150 0.01113 0.00413 -0.0558 0.6858 0.5403
-2.250 0.0423 0.01108 0.00408 -0.0556 0.6769 0.5631
-2.000 0.0696 0.01106 0.00401 -0.0554 0.6692 0.5838
-1.750 0.0970 0.01105 0.00395 -0.0552 0.6606 0.6022
-1.500 0.1245 0.01105 0.00389 -0.0550 0.6527 0.6183
-1.250 0.1519 0.01105 0.00385 -0.0548 0.6445 0.6331
-1.000 0.1794 0.01105 0.00381 -0.0546 0.6363 0.6468
-0.750 0.2068 0.01106 0.00377 -0.0544 0.6284 0.6599
-0.500 0.2342 0.01107 0.00375 -0.0542 0.6201 0.6723
-0.250 0.2617 0.01110 0.00372 -0.0541 0.6124 0.6846
0.000 0.2892 0.01112 0.00373 -0.0539 0.6039 0.6968
0.250 0.3163 0.01115 0.00371 -0.0537 0.5965 0.7082
0.500 0.3435 0.01117 0.00374 -0.0535 0.5879 0.7198
0.750 0.3706 0.01122 0.00375 -0.0533 0.5803 0.7316
1.000 0.3977 0.01125 0.00379 -0.0531 0.5719 0.7440
1.250 0.4245 0.01130 0.00382 -0.0528 0.5642 0.7564
1.500 0.4511 0.01134 0.00388 -0.0525 0.5560 0.7689
1.750 0.4776 0.01139 0.00394 -0.0522 0.5482 0.7821
2.000 0.5039 0.01145 0.00401 -0.0518 0.5402 0.7959
2.250 0.5300 0.01151 0.00408 -0.0514 0.5323 0.8105
2.500 0.5558 0.01157 0.00417 -0.0509 0.5243 0.8261
2.750 0.5815 0.01164 0.00426 -0.0504 0.5165 0.8430
3.000 0.6072 0.01172 0.00435 -0.0499 0.5086 0.8617
3.250 0.6332 0.01179 0.00447 -0.0495 0.5004 0.8823
3.500 0.6604 0.01188 0.00456 -0.0493 0.4926 0.9053
3.750 0.6913 0.01197 0.00470 -0.0499 0.4838 0.9302
4.000 0.7262 0.01210 0.00482 -0.0515 0.4755 0.9567
4.250 0.7637 0.01223 0.00496 -0.0537 0.4659 0.9866
4.500 0.7926 0.01241 0.00512 -0.0543 0.4576 1.0000
4.750 0.8174 0.01261 0.00530 -0.0539 0.4493 1.0000
5.000 0.8425 0.01281 0.00549 -0.0536 0.4408 1.0000
5.250 0.8673 0.01304 0.00568 -0.0533 0.4328 1.0000
5.500 0.8925 0.01324 0.00591 -0.0530 0.4238 1.0000
5.750 0.9172 0.01349 0.00615 -0.0526 0.4157 1.0000
6.000 0.9418 0.01373 0.00640 -0.0523 0.4067 1.0000
6.250 0.9663 0.01399 0.00666 -0.0519 0.3981 1.0000
6.500 0.9903 0.01426 0.00694 -0.0514 0.3895 1.0000
6.750 1.0144 0.01454 0.00726 -0.0510 0.3805 1.0000
7.000 1.0378 0.01485 0.00756 -0.0505 0.3720 1.0000
7.250 1.0611 0.01515 0.00790 -0.0499 0.3625 1.0000
7.500 1.0840 0.01547 0.00825 -0.0494 0.3537 1.0000
7.750 1.1061 0.01583 0.00863 -0.0486 0.3448 1.0000
8.000 1.1284 0.01617 0.00903 -0.0480 0.3354 1.0000
8.250 1.1495 0.01656 0.00944 -0.0471 0.3265 1.0000
8.500 1.1696 0.01697 0.00987 -0.0462 0.3161 1.0000
8.750 1.1890 0.01739 0.01034 -0.0451 0.3045 1.0000
9.000 1.2068 0.01785 0.01082 -0.0438 0.2925 1.0000
9.250 1.2233 0.01836 0.01134 -0.0424 0.2805 1.0000
9.500 1.2374 0.01890 0.01189 -0.0406 0.2676 1.0000
9.750 1.2486 0.01950 0.01249 -0.0384 0.2553 1.0000
10.000 1.2596 0.02016 0.01318 -0.0363 0.2431 1.0000
10.250 1.2712 0.02086 0.01392 -0.0344 0.2314 1.0000
10.500 1.2817 0.02165 0.01474 -0.0326 0.2199 1.0000
10.750 1.2898 0.02260 0.01570 -0.0306 0.2062 1.0000
11.000 1.2956 0.02374 0.01682 -0.0287 0.1905 1.0000
11.250 1.2983 0.02516 0.01818 -0.0267 0.1730 1.0000
11.500 1.2998 0.02677 0.01973 -0.0248 0.1537 1.0000
11.750 1.2983 0.02871 0.02159 -0.0231 0.1338 1.0000
12.000 1.2958 0.03087 0.02366 -0.0216 0.1152 1.0000
12.250 1.2953 0.03302 0.02580 -0.0204 0.1010 1.0000
12.500 1.2944 0.03531 0.02807 -0.0194 0.0890 1.0000
12.750 1.2924 0.03781 0.03057 -0.0186 0.0781 1.0000
13.250 1.2891 0.04304 0.03586 -0.0176 0.0618 1.0000
13.500 1.2861 0.04595 0.03880 -0.0174 0.0548 1.0000
13.750 1.2816 0.04914 0.04202 -0.0173 0.0483 1.0000
14.000 1.2801 0.05215 0.04511 -0.0175 0.0435 1.0000
14.500 1.2724 0.05904 0.05212 -0.0183 0.0349 1.0000
14.750 1.2663 0.06297 0.05610 -0.0190 0.0311 1.0000
15.000 1.2622 0.06674 0.05998 -0.0199 0.0283 1.0000
15.250 1.2576 0.07071 0.06404 -0.0209 0.0258 1.0000
15.500 1.2502 0.07519 0.06861 -0.0222 0.0239 1.0000
15.750 1.2446 0.07951 0.07305 -0.0235 0.0223 1.0000
16.000 1.2390 0.08396 0.07762 -0.0249 0.0207 1.0000
16.250 1.2326 0.08863 0.08240 -0.0266 0.0195 1.0000
16.500 1.2240 0.09375 0.08760 -0.0285 0.0184 1.0000
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